EP2935835B1 - Wärmemanagement für einen gasturbinenmotor - Google Patents

Wärmemanagement für einen gasturbinenmotor Download PDF

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Publication number
EP2935835B1
EP2935835B1 EP13874584.9A EP13874584A EP2935835B1 EP 2935835 B1 EP2935835 B1 EP 2935835B1 EP 13874584 A EP13874584 A EP 13874584A EP 2935835 B1 EP2935835 B1 EP 2935835B1
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EP
European Patent Office
Prior art keywords
gas turbine
turbine engine
vehicle
set forth
outer casing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13874584.9A
Other languages
English (en)
French (fr)
Other versions
EP2935835A4 (de
EP2935835A2 (de
Inventor
Anthony C. Jones
Charles Brian Travelbee
Patrick M. Lydon
Eric J. Alexander
Nagamany Thayalakhandan
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
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Filing date
Publication date
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Publication of EP2935835A2 publication Critical patent/EP2935835A2/de
Publication of EP2935835A4 publication Critical patent/EP2935835A4/de
Application granted granted Critical
Publication of EP2935835B1 publication Critical patent/EP2935835B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling
    • B64U20/96—Cooling using air
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/10—Missiles having a trajectory only in the air
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0273—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for jet engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This application relates to a miniature gas turbine engine, which is used to power an aircraft, such as a drone or ballistic missile.
  • Miniature gas turbine engines are utilized to power aircraft such as unmanned drones, or ballistic missiles. These gas turbine engines generate very high heat, and travel at a high speed.
  • An air scoop delivers inlet air directly into a compressor in the miniature gas turbine engine.
  • a prior art gas turbine engine having the features of the preamble to claim 1 is disclosed in US 2009/0214331 A .
  • Other prior art gas turbine engines are disclosed in US 3,032,977 , WO 03/037715 , US 7,475,545 and GB 2,152,147 .
  • Another gas turbine engine is disclosed in WO 2014/092750 , which is prior art under Article 54(3) EPC.
  • the present invention provides a gas turbine engine in accordance with claim 1.
  • the gas turbine engine includes a compressor that compresses air and delivers it into a combustion section where it is mixed with fuel and ignited.
  • the products of the combustion pass downstream over a turbine rotor driving the turbine rotor to rotate.
  • the gases downstream of the turbine rotor pass outwardly of a nozzle to provide propulsion for the vehicle.
  • the cooling air exits at a downstream end adjacent the nozzle.
  • the present invention provides a vehicle in accordance with claim 4.
  • an outer casing for the vehicle is spaced radially away from the outer casing of the gas turbine engine.
  • the cooling airflow passes between an inner surface of the vehicle outer casing and the outer casing of the gas turbine engine.
  • the vehicle is an unmanned drone.
  • the vehicle carries a ballistic missile.
  • the compressor compresses air and delivers it into a combustion section where it is mixed with fuel and ignited. Products of the combustion pass downstream over a turbine rotor, and drive the turbine rotor to rotate. The gases downstream of the turbine rotor pass outwardly of a nozzle to provide propulsion for the vehicle.
  • the cooling air exits adjacent the nozzle.
  • Figure 1 shows miniature gas turbine engine 26 associated with a vehicle 20.
  • Vehicle 20 includes a main body 22, and aerodynamic surfaces 24 and 25.
  • the vehicle 20 may be utilized as an aircraft drone, or may be utilized as a ballistic missile. Other applications may come within the scope of this application.
  • An air inlet duct 28 supplies air into the gas turbine engine 26.
  • the gas turbine engine operates to compress the air, mix the air with fuel, combust it, and pass products of that combustion across at least one turbine rotor.
  • the turbine rotor is driven to rotate to drive a compressor.
  • the products of the combustion pass outwardly of a nozzle 30 downstream of the turbine section, and provide propulsion for the vehicle 20.
  • miniature gas turbine engine generally relates to gas turbine engines which have an axial length of less than 15 inches (38.1 centimeters), and which provide 180 foot pounds (244 Nm) of thrust or less.
  • the inlet duct 28 delivers airflow into an inlet for a compressor in the miniature gas turbine engine 26.
  • FIG. 2 shows an embodiment of a miniature gas turbine engine 100.
  • an inlet 128 delivers air into a core inlet 130 delivering the air into a compressor rotor 138. That air is compressed in the compressor rotor 138, mixed with fuel and ignited in a combustion section 140 and products of that combustion pass over at least one turbine rotor 142.
  • the turbine rotor 142 drives a compressor rotor 138.
  • An outlet nozzle 148 delivers the products of the combustion downstream of the turbine rotor outwardly to provide thrust for a vehicle such as vehicle 20.
  • An inlet duct 134 curves outwardly at a downstream end 133, and delivers cooling air 132 into a gap between an outer casing 136 of the gas turbine engine, and an inner surface of a casing 129 of the vehicle 20 of FIG. 1 .
  • This airflow passes downstream outwardly at the nozzle end 150.
  • This airflow passes over one or more components 146 to cool those components.
  • the components 146 are at least one of actuators or electronic controls.
  • the gas turbine engine 100 By utilizing a portion of the air entering the inlet 128, the gas turbine engine 100 simply provides cooling to the components.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Remote Sensing (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Gasturbinenmotor (100), umfassend einen Einlasskanal (128), wobei der Einlasskanal (128) konfiguriert ist, um mit einem Einlass (130) zu einem Verdichter (138) zu kommunizieren, wobei die axiale Länge des Gasturbinenmotors (100) weniger als 38,1 Zentimeter (15 Zoll) ist, und der Gasturbinenmotor (100) 244 Nm (180 Foot-pound) Schub oder weniger bereitstellt, dadurch gekennzeichnet, dass
    der Einlasskanal (128) ferner konfiguriert ist, um Kühlluft (132) außerhalb eines Außengehäuses (136) des Gasturbinenmotors (100) zu kommunizieren, und um die Luft (132) entlang einer axialen Länge des Gasturbinenmotors (100) zu leiten, um eine Komponente (146) zu kühlen, die mit dem Gasturbinenmotor (100) verbunden ist; und
    der Einlasskanal (128) einen Verteiler (134) aufweist, der an einem stromabwärtigen Ende (133) radial nach außen gebogen ist, um zu ermöglichen, dass die Luft (132) entlang des Außengehäuses (136) des Gasturbinenmotors (100) strömt,
    und dass die Komponente (146) zumindest eines von einem Aktor oder einer elektronischen Steuerung beinhaltet.
  2. Gasturbinenmotor nach einem vorhergehenden Anspruch, wobei der Gasturbinenmotor (100) den Verdichter (138) beinhaltet, der Luft (132) verdichtet und sie in einen Brennkammerabschnitt (140) abgibt, wo sie mit Kraftstoff vermischt und gezündet wird, wobei die Produkte der Verbrennung stromabwärts über einen Turbinenrotor (142) geleitet werden, wodurch der Turbinenrotor (142) angetrieben wird, sodass er sich dreht, wobei die Gase stromabwärts des Turbinenrotors (142) außerhalb einer Düse (148) geleitet werden, um Antrieb für ein Fahrzeug bereitzustellen.
  3. Gasturbinenmotor nach Anspruch 2, wobei die Kühlluft (132) an einem stromabwärtigen Ende benachbart zu der Düse (148) austritt.
  4. Fahrzeug, umfassend:
    eine Karosserie, die zumindest eine aerodynamische Fläche aufweist; und
    den Gasturbinenmotor (100) nach Anspruch 1.
  5. Fahrzeug nach Anspruch 4, wobei ein Außengehäuse (129) für das Fahrzeug radial weg von dem Außengehäuse (136) des Gasturbinenmotors (100) beabstandet ist und der Kühlluftstrom (132) zwischen einer Innenfläche des Fahrzeugaußengehäuses (129) und dem Außengehäuse (136) des Gasturbinenmotors (100) geleitet wird.
  6. Fahrzeug nach Anspruch 4 oder 5, wobei das Fahrzeug eine unbemannte Drohne ist.
  7. Fahrzeug nach Anspruch 4, 5 oder 6, wobei das Fahrzeug eine ballistische Rakete trägt.
  8. Fahrzeug nach einem der Ansprüche 4 bis 7, wobei der Verdichter (138) Luft verdichtet und sie in einen Brennkammerabschnitt (140) abgibt, wo sie mit Kraftstoff vermischt und gezündet wird, und Produkte der Verbrennung stromabwärts über einen Turbinenrotor (142) geleitet werden, wodurch der Turbinenrotor (142) angetrieben wird, sodass er sich dreht, und die Gase stromabwärts des Turbinenrotors (142) außerhalb einer Düse (148) verlaufen, um Antrieb für das Fahrzeug bereitzustellen.
  9. Fahrzeug nach Anspruch 8, wobei die Kühlluft (132) benachbart zu der Düse (148) austritt.
EP13874584.9A 2012-12-19 2013-12-17 Wärmemanagement für einen gasturbinenmotor Active EP2935835B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/719,706 US20140208714A1 (en) 2012-12-19 2012-12-19 Thermal Management for Gas Turbine Engine
PCT/US2013/075623 WO2014123626A2 (en) 2012-12-19 2013-12-17 Thermal management for gas turbine engine

Publications (3)

Publication Number Publication Date
EP2935835A2 EP2935835A2 (de) 2015-10-28
EP2935835A4 EP2935835A4 (de) 2015-12-23
EP2935835B1 true EP2935835B1 (de) 2019-10-09

Family

ID=51221424

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13874584.9A Active EP2935835B1 (de) 2012-12-19 2013-12-17 Wärmemanagement für einen gasturbinenmotor

Country Status (3)

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US (1) US20140208714A1 (de)
EP (1) EP2935835B1 (de)
WO (1) WO2014123626A2 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10934938B2 (en) * 2016-07-22 2021-03-02 Raytheon Technologies Corporation Boundary layer cooling air for embedded engine
US11262077B2 (en) 2019-09-20 2022-03-01 Raytheon Technologies Corporation Spall plate for consumable combustor support structures

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090214331A1 (en) * 2008-02-22 2009-08-27 Hamilton Sundstrand Corporation Curved tooth coupling for a miniature gas turbine engine

Family Cites Families (9)

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Publication number Priority date Publication date Assignee Title
US3032977A (en) 1958-06-05 1962-05-08 Gen Electric Correlated bypass inlet and outlet control for a supersonic reaction powerplant
US4608819A (en) 1983-12-27 1986-09-02 General Electric Company Gas turbine engine component cooling system
US5070690A (en) * 1989-04-26 1991-12-10 General Electric Company Means and method for reducing differential pressure loading in an augmented gas turbine engine
US5056307A (en) * 1990-05-25 1991-10-15 The United States Of America As Represented By The Secretary Of The Air Force Exhaust nozzle cooling utilizing total engine flow
US5623823A (en) * 1995-12-06 1997-04-29 United Technologies Corporation Variable cycle engine with enhanced stability
US6651929B2 (en) 2001-10-29 2003-11-25 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
US7475545B2 (en) * 2005-04-29 2009-01-13 General Electric Company Fladed supersonic missile turbojet
US8082727B2 (en) * 2008-02-26 2011-12-27 United Technologies Corporation Rear propulsor for a variable cycle gas turbine engine
US9909504B2 (en) 2012-12-13 2018-03-06 United Technologies Corporation Gas turbine engine with cooling scheme for drive gear system and pitch control

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090214331A1 (en) * 2008-02-22 2009-08-27 Hamilton Sundstrand Corporation Curved tooth coupling for a miniature gas turbine engine

Also Published As

Publication number Publication date
WO2014123626A3 (en) 2014-11-20
EP2935835A4 (de) 2015-12-23
US20140208714A1 (en) 2014-07-31
EP2935835A2 (de) 2015-10-28
WO2014123626A2 (en) 2014-08-14

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